# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 1 of 45 Embraer Copyright © 2011. All rights reserved. Copyright © 2011 by EMBRAER S.A. All rights reserved.



### STABILIZERS – IMPROVEMENT IN LIGHTN ING PROTECTION OF THE TAIL BOOM

1. PLANNING INFORMATION
A. SB EFFECTIVITY
Aircraft affected:
MODEL SN
EMB-135BJ 145412, 145462, 145484, 145495, 145505, 145516, 145528, 145540, 145549, 145555, 145586, 145625, 145637, 145642, 145644, 145678, 145686, 145699, 145706, 145711, 145717, 145730, 145770, 145775, 145780, 145789, 145796, 14500802, 14500809, 14500818, 14500825, 14500832, 145008 41, 14500851, 14500854, 14500863, 14500867, 145008 73, 14500880, 14500884, 14500891, 14500901, 14500903, 14500910, 145009 13, 14500916, 14500919, 14500925, 14500933, 14500937, 145009 39, 14500941, 14500942, 14500944, 14500946, 14500948, 145009 50, 14500952, 14500954, 14500955, 145009 57, 14500960, 14500961, 14500963, 14500965 thru 14500967, 14500969 th ru 14500976, 14500978 thru 14500983, 14500985, 14500986, 14500988 thru 14500991, 14500993 thru 14500995, 14500997 th ru 14500999, 14501001 thru 14501004, 14501006 thru 14501008, 14501010 thru 14501012, 14501014 thru 14501018, 145010 20, 14501021, 14501023, 14501025, 14501026, 14501029, 14501031, 145010 32, 14501034, 14501035, 14501037 thru 14501039, 14501041, 14501042, 14501044 thru 14501046, 145010 48, 14501049, 14501051, 14501052, 14501054, 14501055, 14501057, 14501058, 14501060 thru 14501062, 14501064, 14501066 , 14501067, 14501069, 14501071, 14501072, 14501074, 145 01075, 14501078 thru 14501080, 14501082, 145010 83, 14501086, 14501087, 14501089 thru 14501091, 14501094 thru 14501096, 14501098 thru 14501100, 14501102, 14501105 thru 14501107, 14501109 thru 14501111, 14501113, 14501114, 14501117 thru 14501123, 14501126 thru 14501128, 14501131 thru 14501134, and 14501136 thru 14501145.

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 2 REVISION No.: Embraer Copyright © 2011. All rights reserved. 

### In-production effectivity:
EMB-135BJ model aircraft SN 14501092, 14501103, and 14501146 and on, have an equivalent modification factory-incorporated. The SB effectivity is divided into 02 GROUPS of aircraft, as follows: (1) GROUP 1

MODEL SN EMB-135BJ 145412, 145462, 145484, 145495, 1455 05, 145516, 145528, 145540, 145549, 145555, 145586, 145625, 145637, 145642, 145644, 145678, 145686, 145699, 145706, 145711, 145717, 145730, 145770, 145775, 145780, 145789, 14579 6, 14500802, 14500809, 14500818, 145008 25, 14500832, 14500841 , 14500851, 14500854, 14500863, 14500867, 14500873, 14500880, 14500884, 14500891, 14500901, 145009 03, 14500910, 14500913 , 14500916, 14500919, 14500925, 145009 33, 14500937, 14500939 , 14500941, 14500942, 14500944, 145009 46, 14500948, 14500950 , 14500952, 14500954, 14500955, 145009 57, 14500960, 14500961 , 14500963, 14500965 thru 14500967, 14500969 thru 14500976, 14500978 thru 14500983, 14500985, 14500986, 14500988 thru 14500991, 14500993 thru 14500995, 14500997 th ru 14500999, 14501001 thru 14501004, 14501006 thru 14501008, 14501010 thru 14501012, 14501014 thru 14501018, 14501020, 14501021, 14501023, 14501025, 14501026, 145010 29, 14501031, 14501032 , 14501034, 14501035, 14501037 thru 14501039, 14501041, 14501042, 14501044 thru 14501046, 145010 48, 14501049, 14501051, 14501052, 14501054, 14501055, 14501057, 14501058, 14501060 thru 14501062, 14501064, 14 501066, 14501067, 14501069, 14501071, 14501072, 14501074, 145 01075, 14501078 thru 14501080, 14501082, 14501083, 14501086, 14501087, 14501089 thru 14501091, 14501094 thru 14501096, 14501098 thru 14501100, 14501102, 14501105 thru 14501107, 14501109 thru 14501111, 14501113, 14501114, 14501117 thru 14501123, 14501126 thru 14501128, 14501131 thru 14501134, and 14501136 thru 14501145 if equipped with Mo vable Tail Boom With Two Navigation Lights.

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 3 Embraer Copyright © 2011. All rights reserved. 

### (2) GROUP 2

MODEL SN EMB-135BJ 145412, 145462, 145484, 145495, 145505, 145516, 145528, 145540, 145549, 145555, 145586, 145625, 145637, 145642, 145644, 145678, 145686, 145699, 145706, 145711, 145717, 145730, 145770, 145775, 145780, 145789, 145796, 14500802, 14500809, 14500818, 145008 25, 14500832, 14500841, 14500851, 14500854, 14500863, 14500867, 14500873, 145008 80, 14500884, 14500891, 14500901, 14500903, 14500910, 145009 13, 14500916, 14500919, 14500925, 14500933, 14500937, 145009 39, 14500941, 14500942, 14500944, 145009 46, 14500948, 14500950, 14500952, 14500954, 14500955, 14500957, 14500960, 145009 61, 14500963, 14500965 thru 14500967, 14500969 th ru 14500976, 14500978 thru 14500983, 14500985, 14500986, 14500988 thru 14500991, 14500993 thru 14500995, 14500997 th ru 14500999, 14501001 thru 14501004, 14501006 thru 14501008, 14501010 thru 14501012, 14501014 thru 14501018, 145010 20, 14501021, 14501023, 14501025, 14501026, 14501029, 14501031, 145010 32, 14501034, 14501035, 14501037 thru 14501039, 14501041, 14501042, 14501044 thru 14501046, 14501048, 14501049, 14501051, 14501052, 14501054, 145010 55, 14501057, 14501058, 14501060 thru 14501062, 14501064, 14501066 , 14501067, 14501069, 14501071, 14501072, 14501074, 145 01075, 14501078 thru 14501080, 14501082, 145010 83, 14501086, 14501087, 14501089 thru 14501091, 14501094 thru 14501096, 14501098 thru 14501100, 14501102, 14501105 thru 14501107, 14501109 thru 14501111, 14501113, 14501114, 14501117 thru 14501123, 14501126 thru 14501128, 14501131 thru 14501134, and 14501136 thru 14501145 if equipped with Movable Tail Boom With Four Navigation Lights.

B. CONCURRENT REQUIREMENTS The accomplishment of Servic e Bulletin SB145LEG- 33-0004 in its orig inal Issue or a subsequent approved revision is required prior to the accomplishment of this Service Bulletin.

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 4 REVISION No.: Embraer Copyright © 2011. All rights reserved. 

### C. REASON (1) HISTORY During a troubleshooting following a report ed of elevator control restriction the maintenance personnel f ound a frame loosed from the tail boom jamming a bellcrank. Further investigation rev ealed that this damage was caused by a lightning-strike that hit the tail boom area.

(2) OBJECTIVE To install lightning diverters in the ta il boom, replace the hood assembly with a new improved one and reroute the electrical harness.

(3) EXPECTED BENEFITS To improve the electrical path for t he lightning current, thereby minimizing lightning direct effects on the aircraft.

(4) REVISION HISTORY None.

D. DESCRIPTION
The modification described of this bulletin c onsists of the installation of metallic diverters, aluminum sheets and improvements on lights a ssembly on the tail boom rear movable fairing, and also to replac e the hood assembly with new one and reroute the applicable electrical harness to minimize lightning direct effects. To do this, it is necessary to remove t he rear movable fairing of the tail boom.

E. COMPLIANCE
Embraer recommends that this bulleti n be accomplished during the scheduled maintenance check of 48 months.

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 5 Embraer Copyright © 2011. All rights reserved. 

### F. APPROVAL The technical aspects of this Service Bulletin are approved by: ANAC – Agência Nacional de Aviação Civil.

G. ESTIMATED MANPOWER This estimate is for direct labor only, per formed by experienced personnel, and does not include the time to plan, prepare, or inspect the work. It is assumed that all the tools, parts, and other means are prom ptly available when necessary. This estimate does not include the s ealant, paint, or adhesive curing time.

- Access opening: 1.5 man-hours.

- Inspection: None.

- Modification: 5.5 man-hours.

- Access closure: 1.5 man-hours.

- Test: 1.0 man-hour.

H. WEIGHT AND BALANCE

- Change in basic weight: None

- Change in basic moment: None

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 6 REVISION No.: Embraer Copyright © 2011. All rights reserved. 

### I. ELECTRICAL LOAD DATA
Not affected.

J. REFERENCES AMM 145/( ) – Aircraft Maintenance Manual – Chapter 20-13-21 – Standard Practices - Airframe. AMM 145/( ) – Aircraft Maintenance Manual – Chapter 55-36-05 – Stabilizers. SRM 145/( ) – Structural Repair Manual – Chap ter 51-20-01 and 51-40-04 – Standard Practices and Structures.

K. OTHER PUBLICATIONS AFFECTED IPC 145/( ) – Illustrated Parts Cata log – Chapter 55-36-00 – Stabilizers. AMM 145/( ) – Aircraft Maintenance Manual – Chapter 55-36-00 – Stabilizers.

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 7 Embraer Copyright © 2011. All rights reserved. 

### 2. MATERIAL INFORMATION
A. MATERIAL – PRICE AND AVAILABILITY (1) MATERIAL AVAILABLE FROM EMBRAER The material below required for the a ccomplishment of this bulletin will be available from Embraer. Lead Times for delivery are conservati ve and are estimated from the date Embraer gets the purchase order. The prices are for reference only, subjec t to confirmation upon receipt of orders. When ordering, specify SB 145LEG-55-0013 and Top Kit PN presented in Table below, as applicable.

REF TOP KIT PN Lead Time (weeks) Unit Price (US$) TOP KIT EFFECTIVITY
01 BSLEG5500130001 08 1.251,36 GROUP 1. 02 BSLEG5500130002 08 1.227,84 GROUP 2.



### (2) MATERIAL AVAILABLE FROM OTHER VENDORS
None.

B. INDUSTRY SUPPORT INFORMATION (1) WARRANTY COVERAGE (a) Parts The SB kit will be provided at no charge.

(b) Labor Embraer will compensate 9,5 hours for the SB incorporati on if it is performed in an Embraer authorized service center.

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 8 REVISION No.: Embraer Copyright © 2011. All rights reserved. 

### (c) Expiration The terms expressed in the warranty cove rage will be valued for 48 months after the SB issue date.

C. MATERIAL NECESSARY FOR EACH AIRCRAFT When applicable, the use of alternative or similar parts in place of the ones specified in the kit is allowable, prov ided that these alternative or similar parts are approved by Embraer. Refer to IPC Optional PN Cross-Reference List. The expendable or consumable parts presented in the AMM Tasks referred to in this bulletin, which are necessary for its a ccomplishment, should be procured from the operator's inventories or ordered as spares. The complementary information, when nece ssary, is presented as Notes in the respective Table.

(1) TOP KITS AND KITS Kit Summary: Top Kit Composit ion (Kit PN / Quantity) Top Kit PN 145-03536-611 14 5-54608-607 14 5-03535-621 BSLEG5500130001 01 01

- BSLEG5500130002 - 01 01

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 9 Embraer Copyright © 2011. All rights reserved. 

### (a) Kit PN 145-03536-611 - Electrical kit for Tail Boom With two Navigation Lights

NEW PN DESCRIPTION OLD PN QTY SUP QTY RQD DISP/ Notes 145-23046-403 Hood assy 145-23046-401 01 01 3 H14-04 Nut H14-04 02 02 7 H14-08 Nut - 02 02 2 MS24693-C6 Screw - 02 02 2 MS24694-C6 Screw - 02 02 2 MS35206-214 Screw MS35206-214 02 02 7 MS35338-40 Lock washer MS35338-40 04 04 7 MS35489-8 Grommet MS35489

− 8 01 01 7 NAS1149CN832R Washer - 01 01 2 NAS1149FN416P Washer NAS1149FN416P 04 04 7 NAS1149FN832P Washer - 02 02 2 NAS1197-4L Washer NAS1197-4L 04 04 7 NAS1801-08-8 Screw - 01 01 2 PE21101-3-1CP Screw PE21101

− 3

− 2CP 07 07 3 PE21101-3-2CP Screw - 06 06 2 PE27019RI5 Clamp, chushion - 03 03 2 PE88001-5AA8 Jumper assy PE88001

− 5AA6 02 02 3



### (b) Kit PN 145-54608-607 – Rework ki t for rear movable fairing

NEW PN DESCRIPTION OLD PN QTY SUP QTY RQD DISP/ Notes 145-54611-004 Lightning sheet - 01 01 2 145-54611-005 Lightning sheet - 01 01 2 145-54614-003 Lightning diverter - 01 01 2 145-54614-007 Lightning diverter - 02 02 2 145-54614-009 Lightning diverter - 01 01 2 CCR244CS-3-2 Blind rivet csk 100 deg - 75 62 2 MS20426AD3-4 Solid rivet csk 100 deg - 11 08 2 MS20426AD3-5 Solid rivet csk 100 deg - 11 08 2 MS20426AD4-7 Solid rivet csk 100 deg - 04 02 2 MS21060L3 Nut plate - 30 27 2 MS21062L3 Nut plate - 05 04 2

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 10 REVISION No.: Embraer Copyright © 2011. All rights reserved. NEW PN DESCRIPTION OLD PN QTY SUP QTY RQD DISP/ Notes NAS620A5L Washer - 26 20 2 NAS9301B-4-05 Blind rivet - 02 01 2 NAS9302B-4-02 Blind rivet csk 100 deg - 02 01 2 NAS9302B-4-03 Blind rivet csk 100 deg - 24 18 2 PE21101-3-2CP Screw - 34 31 2 PE29051Z-3CH Support assy - 01 01 2 - Support TW2S6 01 01 5 - Support MS3340-1-9 01 01 5



### (c) Kit PN 145-03535-621 – Electrical kit for Tail Boom With four Navigation Lights

NEW PN DESCRIPTION OLD PN QTY SUP QTY RQD DISP/ Notes 145-23046-403 Hood assy 145-23046-401 01 01 3 H14-04 Nut H14-04 02 02 7 H14-08 Nut - 02 02 2 MS24693-C6 Screw - 02 02 2 MS24694-C6 Screw - 02 02 2 MS35338-40 Lock washer MS35338-40 02 02 7 MS35489-8 Grommet MS35489-8 01 01 7 NAS1149CN832R Washer - 01 01 2 NAS1149FN416P Washer NAS1149FN416P 02 02 7 NAS1149FN832P Washer - 02 02 7 NAS1197-4L Washer NAS1197-4L 02 02 7 NAS1801-08-8 Screw - 01 01 2 PE21101-3-1CP Screw PE21101

− 3

− 2CP 07 07 3 PE21101-3-2CP Screw - 06 06 2 PE27019RI5 Clamp, cushion - 03 03 2



### (2) MATERIAL TO BE PROCURED (a) Parts None.

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 11 Embraer Copyright © 2011. All rights reserved. 

### (b) Consumables The material below or equivalent, requi red for the accomplishment of this bulletin, should be procured from the operator’s invent ories or from a local supplier.

ITEM PN DESCRIPTION QTY DISP/ Notes 

### P/S870C-12 Sealant (Spec. MIL-PRF-81733) AR 6 

### PR1440B2 Sealant (Spec. SAE AMS-S-8802) AR 6 

### PR1776M B2 654 SEMKIT Sealant (Spec. AMS3281) AR 6 

### PR1776M B1/2 654 SEMKIT Sealant (Spec. AMS3281) AR 6


### SB496 Cyanoacrylate adhesive (Spec. MEP 09-033) AR 6
P/S870-B1/2 Sealant (Spec. MIL-PRF-81733) AR 6


### ALODINE 1200S Chemical Conversion Compound (Spec. MIL-DTL-81706) AR 6



### QUANTITY : AR = As Required.
DISPOSITION : 2 = Incorporate part bearing NEW PN 3 = Replace part bearing OLD PN with part bearing NEW PN 6 = Apply as required 7 = Replace with part bearing same PN

D. MATERIAL NECESSARY FOR EACH SPARE
None.

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 12 REVISION No.: Embraer Copyright © 2011. All rights reserved. 

### E. REIDENTIFIED PARTS The information necessary to modify and/or reidentify the parts, when necessary, is presented in the referenced Notes.
DESCRIPTION OLD PN NEW PN 145-53615-403 145-21648-433 Movable Tail Boom fairing assy 145-03536-401 145-03536-603 Movable Tail Boom fairing assy 145-03535-401 145-03535-603 Movable Tail Boom fairing assy 145-03535-409 145-03535-617 145-38445-403 Movable Tail Boom fairing assy 145-38445-407 145-03535-413 Movable Tail Boom fairing 145-21649-417 Movable Tail Boom fairing 145-21649-419 140-13327-601

F. TOOLING – PRICE AND AVAILABILITY Whenever required, the too ling presented in the AMM Tasks referred to in this bulletin, should be procured fr om the operator’s inventor ies or ordered as spares.

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 13 Embraer Copyright © 2011. All rights reserved. 

### 3. ACCOMPLISHMENT INSTRUCTIONS
NOTES : 1) Obey all of the WARNINGS and CAUTIONS included in the referenced manuals and procedures. 2) The Manuals and other documents are referred to by means of acronyms or using a simplified form. Refer to section “1. I. REFERENCES” for a more complete definition.
The steps below outline the general accomplishment instructions. The detailed sequence is included in t he respective figure, when necessary.

A. Make sure that the airc raft is safe for maintenance. B. Remove the rear movable fairing of t he tail boom. Refer to the applicable Aircraft Maintenance Manual – Chapt er 55-36-00 – Stabilizers. C. Rework the movable fairing of the tail boom according Figure 1. D. Carry out the electrical modification to the rear movable fairi ng according Figure 2 (GROUP 1) or Figure 3 (G ROUP 2), as applicable.
E. Reinstall the rear movable fairing of the tail boom according to the applicable Aircraft Maintenance Manual – Chapter 55-36-00 – Stabilizers, and pe rform the following electrical bonding test:

a Do the electrical bonding test accordi ng to the applicable Aircraft Maintenance Manual – Chapter 20 (TASK 20-13-21- 700-801-A) – Standard Practices – Airframe.
NOTE: Measure the electrical resistan ce value between the electrical connector P0834 and the primary st ructure. The maximum allowed resistance value is 15 miliohms.
F. Paint the reworked area with customer ’s color scheme. Refer to Corrosion Prevention Manual, Chapter 51-21-06.

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 14 REVISION No.: Embraer Copyright © 2011. All rights reserved. 

### G. Restore the aircraft to normal. H. Enter the accomplishment of this bulletin in the applicable documents.
I. Fill out the attached “Service Bulletin Implementation and Evaluation” form and return it to: EMBRAER S.A. Customer Support Contact Center Embraer Executive Jets contact.center@embraer.com
24/7 Toll Free Numbers 1 888 362-2648 USA & Canada 0800 704 1099 Brazil
24/7 International Numbers 1 703 621-7350 North America, in cluding Mexico, & Caribbean +33 1 7048-0510 Europe, Middle East & Africa +65 6307-7647 Asia Pacific +55 12 3927-7000 Latin America
NOTE : To formally inform that the SB has been inco rporated in the airc raft or that the SB will not be incorporated, so that Em braer can update the affected technical publications, use the “Service Bulletin Full-Fleet Incorpor ation Report” form, which is available on the Flyembraer portal ( http://www.flyembraer.com ).

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 15 Embraer Copyright © 2011. All rights reserved. 

### 1. Position sheets PN 1 45-54611-004 (RH) and PN 145-54611- 005 (LH) on the rear movable fairing and transfer the existing hole s from fairing to sheet and from sheet to fairing, using the dimension shown in view B and G as a guide.
2. Drill the holes marked in step 1.
3. Countersink sheets PN 145-54611-004 (RH) and PN 145-54611-005 (LH) to install screws and rivets according to the dimensions shown in detail D. 4. Install nut plate PN MS 21062L3 (4 positions) by using rivet PN CCR244CS-3-2 (2 positions). Refer to details D and H.
5. Install sheets PN 14 5-54611-004 (RH) and PN 145-54611-005 (LH) to the rear movable fairing by using rivet PN NAS 9302B-4-03 (18 positions) and washer PN NAS620A5L (18 positions). Refer to details C and D.
NOTE : Before installation, apply interfac e sealant PN P/S870C-12 (Spec. MILPRF-81733 Type IV Class 12) and fillet sealant PN PR1440B2 (Spec. SAE AMS-S-8802 Type II Class B2). Refer to the applicable Stru ctural Repair Manual – Chapter 51-20-01 – Standar d Practices and Structures. 6. Install support PN PE29051Z-3CH to the re ar movable fairing according to sections J-J and K-K, and details L and L1 and the following instructions: (a) Remove and discard existing support PN MS3340-1-9. (b) Plug the hole with rivet PN NAS9301B-4-05. (c) Position new support PN PE29051Z-3 CH on the rear movable fairing. (d) Transfer, drill and countersink the hole. (e) Install the support using rive t PN MS20426AD4-7 (2 positions). 7. Position diverters PN 145-54614-003 (1 pos ition), PN 145-54614-009 (1 position), and PN 145-54614-007 (2 positions) on the r ear movable fairing, mark and drill holes in the fairing using the existing ho les of the diverters and the dimensions shown in details C, D, E and F as a guide.
8. Remove the diverters and install nut plate PN MS21060L3 (27 positions) from the rear movable fairing using rivet PN CCR244CS -3-2 (54 positions). Refer to detail D.

- APPLICABLE TO GROUP 1 AND GROUP 2
FIGURE 1: IMPROVEMENT IN THE LIGHTN ING PROTECTION OF THE TAIL BOOM (SHEET 01 OF 13)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 16 REVISION No.: Embraer Copyright © 2011. All rights reserved. 

### 9. Install diverters PN 145-54614-003 (1 position), PN 145-54614-009 (1 position), and PN 145-54614-007 (2 positions) to the rear movable fairin g using screw PN PE21101-3-2CP (31 positions). Re fer to details C, E and F.
NOTES : (1) Carry out the electrical bonding according to the applicable Aircraft Maintenance Manual – Chapter 20 (TASK 20-13-21-910-801-A) – Standard Practices - Airframe. (2) Apply fillet sealant PN PR1 440B2 (Spec. SAE AMS-S-8802 Type II Class B2) and interface sealant PN P/S870C-12 (Spec. MIL-PRF81733 Type IV Class 12) except in the surface prepared for electrical bonding shown in the figure. Refer to the applicable Structural Repair Manual – Chap ter 51-20-01 – Standard Practices and Structures. 10. Remove the existing rivet and enlarge the hole to 25.4 mm, as shown in section PP. 11. Remove and discard the existing electr ical support PN TM2S6 by removing its attached rivet. Plug the hole with rive t PN NAS9302B-4-02 and washer PN NAS620A5L. Refer to detail Q.
12. At the stabilizer structur e, remove and retain nut plate PN MS21062L3 (6 positions) and PN MS21060L3 (2 positions) and discard t he attaching rivets. Refer to detail T (PRE MOD) and Structural Repair Ma nual – Chapter 51-40-02 – Standard Procedures.
13. Reinstall the removed nut plates PN MS21062L3 (6 positions) and PN MS21060L3 (2 positions) using rivets PN MS20426AD3-5 (8 positions) and PN MS20426AD3-4 (8 positions) according to detail T (POST MOD). Refer to Structural Repair Manual – Chapter 51-40-02 and 51-40- 03 – Standard Procedures. 14. Apply a fillet of sealan t PN PR1776M B2 654 SEMKIT to the contour of the part. Refer to detail U.

- APPLICABLE TO GROUP 1 AND GROUP 2

FIGURE 1: IMPROVEMENT IN THE LIGHTN ING PROTECTION OF THE TAIL BOOM (SHEET 02 OF 13)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 17 Embraer Copyright © 2011. All rights reserved. 

### 15. With a permanent marker pen or a rubber stamp, re-identify the movable Tail Boom fairing according to the Table, below:

REIDENTIFICATION TABLE

FROM TO
145-21649-417 140-13327-601
145-21649-419 140-13327-601

- APPLICABLE TO GROUP 1 AND GROUP 2

FIGURE 1: IMPROVEMENT IN THE LIGHTN ING PROTECTION OF THE TAIL BOOM (SHEET 03 OF 13)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 18 REVISION No.: Embraer Copyright © 2011. All rights reserved. 

### A ZONE

321



### C **D**

**E DET. A** 

**F**

REAR FIXED FAIRING



### DET. B **B**

**T**

EM145SB550346A.DGN

- APPLICABLE TO GROUP 1 AND GROUP 2
FIGURE 1: IMPROVEMENT IN THE LIGHTN ING PROTECTION OF THE TAIL BOOM (SHEET 04 OF 13)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 19 Embraer Copyright © 2011. All rights reserved. SHEET PN 145−54611−004 (RH) (INSTALL)

2

1 1

1

1

APPLY INTERFACE SEALANT PN P/S870C−12 AND FILLET SEALANT PN PR1440B2. REAR MOVABLE FAIRING (REF.)

1 5 7

7

5 DIVERTER PN 145−54614−007 (INSTALL) 7

DIVERTER PN 145−54614−003 (INSTALL)



### DET. C 1 1

DIVERTER PN 145−54614−007 (INSTALL) 1 7

DIVERTER PN 145−54614−009 (INSTALL)

SHEET PN 145−54611−005 (LH) (INSTALL)

EM145SB550347A.DGN

- APPLICABLE TO GROUP 1 AND GROUP 2
FIGURE 1: IMPROVEMENT IN THE LIGHTN ING PROTECTION OF THE TAIL BOOM (SHEET 05 OF 13)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 20 REVISION No.: Embraer Copyright © 2011. All rights reserved. Y 0.0

SCREW PN PE21101−3−4CP (4 POSITIONS) (INSTALL) SCREW PN PE21101−3−4CP (4 POSITIONS) (INSTALL) 10.0 RIVET PN NAS9302B−4−03 (9 POSITIONS) WASHER PN NAS620A5L (9 POSITIONS) (INSTALL)

RIVET PN NAS9302B−4−03 (9 POSITIONS) WASHER PN NAS620A5L (9 POSITIONS) (INSTALL) 4

2 5 4 2 5

2 3 5 2 3 5



### H

DIMENSION IN mm 

### DET. G Ø5.1 Ø5.3 1.3

RIVET PN CCR244CS−3−2 (2 POSITIONS) (INSTALL) 8 8 9



### DET. H TYPICAL 

### DET. D 

### G **G** NUT PLATE PN MS21060L3 (14 POSITIONS) RIVET PN CCR244CS−3−2 (2 POSITIONS PER NUT PLATE) (INSTALL)

EM145SB550348A.DGN 8

8 NUT PLATE PN MS21062L3 (2 POSITIONS) (INSTALL)

NUT PLATE PN MS21060L3 (13 POSITIONS) RIVET PN CCR244CS−3−2 (2 POSITIONS PER NUT PLATE) (INSTALL) NUT PLATE PN MS21062L3 (2 POSITIONS) (INSTALL)

NUT PLATE PN MS21060L3 (INSTALL) SCREW PN PE21101−3−2CP (INSTALL) 130°

- APPLICABLE TO GROUP 1 AND GROUP 2
FIGURE 1: IMPROVEMENT IN THE LIGHTN ING PROTECTION OF THE TAIL BOOM (SHEET 06 OF 13)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 21 Embraer Copyright © 2011. All rights reserved. ZV 3755.0 ZV 3604.5 X 28135.9

SPAR III X 28644.9 X 29075.0 VT 100%

X 29786.4



### K K **P P N N**  **S S**

**DET. E** 9



### R R **Q**

EM145SB550349A.DGN X 29075.0 VT 100%

X 29786.4

33.0 100.0



### DET. E1 

### E1

DO NOT APPLY SEALANT IN THIS AREA. 6 6 SCREW PN PE21101−3−2CP (13 POSITIONS) (INSTALL)

SCREW PN PE21101−3−2−CP (2 POSITIONS) (INSTALL TOGETHER WITH THE HOOD ASSY)

9

- APPLICABLE TO GROUP 1 AND GROUP 2

FIGURE 1: IMPROVEMENT IN THE LIGHTN ING PROTECTION OF THE TAIL BOOM (SHEET 07 OF 13)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 22 REVISION No.: Embraer Copyright © 2011. All rights reserved. ZV 3755.0 ZV 3604.5

X 28135.9

SPAR III

X 28644.9

X 29075.0

VT 100%

X 29786.4 9 X 29075.0

VT 100%

X 29786.4 100.0



### DET. F1



### F1

DO NOT APPLY SEALANT IN THIS AREA. 6 6

EM145SB550355A.DGN 

### DET. F SCREW PN PE21101−3−2CP (14 POSITIONS) (INSTALL) SCREW PN PE21101−3−2−CP (2 POSITIONS) (INSTALL TOGETHER WITH THE HOOD ASSY)

9 

### S S

DIMENSIONS IN MM

- APPLICABLE TO GROUP 1 AND GROUP 2

FIGURE 1: IMPROVEMENT IN THE LIGHTN ING PROTECTION OF THE TAIL BOOM (SHEET 08 OF 13)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 23 Embraer Copyright © 2011. All rights reserved. Y 0.0

ZV 3755.0

Y 0.0

ZV 3755.0 HARNESS SUPPORT PN MS3340−1−9 EXISTING RIVET (REMOVE AND DISCARD)

6

6 4
NUT PLATE PN MS21062L3 (4 POSITIONS) (INSTALL) RIVET PN NAS9301B−4−05 WASHER PN NAS620A5L (INSTALL)

EM145SB550350A.DGN 

## SECTION J−J **(POST MOD) SECTION J−J** 

**(PRE MOD)**

**K M** 

- APPLICABLE TO GROUP 1 AND GROUP 2

FIGURE 1: IMPROVEMENT IN THE LIGHTN ING PROTECTION OF THE TAIL BOOM (SHEET 09 OF 13)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 24 REVISION No.: Embraer Copyright © 2011. All rights reserved. DIVERTER (REF.) SHEET (REF.) REAR MOVABLE FAIRING (REF.)

NUT PLATE (REF.)



### DET. M TYPICAL



### SECTION N−N 1

Ø6.3 Ø6.1

DIMENSIONS IN MM SHEET (REF.)

REAR MOVABLE FAIRING (REF.) Ø3.4 Ø3.2 1.2

SUPPORT PN PE29051Z−3CH (1 POSITION) RIVET PN MS20426AD4−7 (2 POSITIONS) (INSTALL)

6 SHEET (REF.)

SUPPORT PN PE29051Z−3CH (1 POSITION) RIVET PN MS20426AD4−7 (2 POSITIONS) (INSTALL)

RIVET PN CCR244CS−3−2 (2 POSITIONS) (INSTALL)

EM145SB550351A.DGN 6

141° 86° 

### DET. K **L**

**DET. L** 100°

90°

- APPLICABLE TO GROUP 1 AND GROUP 2

FIGURE 1: IMPROVEMENT IN THE LIGHTN ING PROTECTION OF THE TAIL BOOM (SHEET 10 OF 13)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 25 Embraer Copyright © 2011. All rights reserved. PRE − MOD HARNESS SUPPORT PN TM2S6 EXISTING RIVET (REMOVE AND DISCARD) RIVET PN NAS9302B−4−02 WASHER PN NAS620A5L (INSTALL)

REMOVE THE EXISTING RIVET AND ENLARGE THE HOLE TO DIAMETER 25.4 MM 3

3 Y 0.0

ZV 3755.0

POST − MOD 10

11 11



### DET. Q **DET. Q** 

## SECTION P−P EXISTING RIVET (REMOVE AND DISCARD ENLARGE THE HOLE)

EM145SB550352A.DGN

- APPLICABLE TO GROUP 1 AND GROUP 2

FIGURE 1: IMPROVEMENT IN THE LIGHTN ING PROTECTION OF THE TAIL BOOM (SHEET 11 OF 13)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 26 REVISION No.: Embraer Copyright © 2011. All rights reserved. 2 2 100° Ø 8.5

2 100° Ø 8.5 

## SECTION R−R

DIMENSION IN mm 

## SECTION S−S **TYPICAL**

APPLY ALODYNE ON THE COUNTERSINK AREA FOR BONDING. (LH SIDE SHOWN, RH SIDE OPPOSITE)

EM145SB550353A.DGN 4.0 ± 0.1

4.6 ± 0.1

- APPLICABLE TO GROUP 1 AND GROUP 2

FIGURE 1: IMPROVEMENT IN THE LIGHTN ING PROTECTION OF THE TAIL BOOM (SHEET 12 OF 13)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 27 Embraer Copyright © 2011. All rights reserved. (PRE−MOD)

1 APPLY A FILLET OF SEALANT PN PR1776M B2 654 SEMKIT TO THE CONTOUR OF THE PART. (POST−MOD) 

### U

**DET. U** 1



## DET. T **DET. T**

EM145SB550354A.DGN SUPPORT (APPLY SEALANT)

14 Y 0.0 YH 30.0 YH −30.0

1

1 1 1
NUT PLATE PN MS21060L3 (RETAIN) NUT PLATE PN MS21060L3 (RETAIN)

NUT PLATE PN MS21062L3 (3 POSITIONS) (RETAIN) NUT PLATE PN MS21062L3 (3 POSITIONS) (RETAIN)

13

13

13 13

13 NUT PLATE PN MS21062L3 (2 POSITIONS) (REINSTALL) RIVET PN MS20426AD3−4 (4 POSITIONS) (INSTALL) NUT PLATE PN MS21062L3 (REINSTALL) RIVET PN MS20426AD3−5 (2 POSITIONS) (INSTALL) NUT PLATE PN MS21060L3 (REINSTALL) RIVET PN MS20426AD3−5 (2 POSITIONS) (INSTALL)

13 NUT PLATE PN MS21060L3 (REINSTALL) RIVET PN MS20426AD3−5 (2 POSITIONS) (INSTALL)

NUT PLATE PN MS21062L3 (REINSTALL) RIVET PN MS20426AD3−5 (2 POSITIONS) (INSTALL)

NUT PLATE PN MS21062L3 (2 POSITIONS) (REINSTALL) RIVET PN MS20426AD3−4 (4 POSITIONS) (INSTALL)

- APPLICABLE TO GROUP 1 AND GROUP 2

FIGURE 1: IMPROVEMENT IN THE LIGHTN ING PROTECTION OF THE TAIL BOOM (SHEET 13 OF 13)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 28 REVISION No.: Embraer Copyright © 2011. All rights reserved. 

### 1. Remove and discard hood assembly PN 145-23046-401 by removing screw PN PE21101-3-2CP (9 positions). Refer to detail B. 2. Disconnect electrical connectors P0707, P0708, and P0715. Refer to detail B (PRE MOD). 3. Remove and discard grommet PN MS 35489-8. Refer to deta il A (PRE MOD). 4. Remove and discard bonding jumper PN PE88001-5AA6 (2 positions) by removing screw PN MS35206-216 and PN MS35206-214, washer PN NAS1149FN416P (2 positions per bonding jumper), PN MS 35338-40 (2 positions per bonding jumper), and PN NAS1197-4L (3 positions per bonding ju mper), and nut PN H14-04. Refer to detail B (PRE MOD) and se ction C-C (PRE MOD).
5. Reroute electrical harness W308 and in stall clamp PN PE27019RI5 with screw PN NAS1801-08-8, washer PN NAS1149CN832R, and clam p PN PE27019RI5 with screw PN MS24694-C6, washer PN NAS1149FN832 P, and nut PN H14-08. Refer to Detail A (Post-Mod). 6. Install grommet PN MS35489-8 with cyanoac rylate adhesive PN SB496. Fill gaps and free spaces with sealant PN PR17 76M B1/2 654 SEMKIT (Spec AMS 3281, class B), or similar. Refer to detail D. 7. Install new bonding jumper PN PE8800 1-5AA8 using screw PN MS35206-214 and PN MS24693-C6, washer PN MS35338-40 (2 positions per bonding jumper), PN NAS1149FN416P (2 positions per bonding jumper), and PN NAS1197-4L (2 positions per bonding Jumper), and nut PN H 14-04. Refer to detail B, and section DD (PRE MOD) and E-E.
NOTE : Carry out the electrical bonding proc edure, method 3. Refer to the applicable Aircraft Maintenance Manual - Chapter 20-13-21 - Standard Practices - Airframe.

- APPLICABLE TO GROUP 1
FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 01 OF 09)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 29 Embraer Copyright © 2011. All rights reserved. 

### 8. Connect electrical connectors P0707, P0 708, and P0715. Refer to detail B (POST MOD).

9. Install hood assembly PN 145-23046-403 between diverters and fairing with screws PN PE21101-3-1CP (7 positi ons) and PN PE21101-3-2CP (6 positions). Refer to detail B (POST MOD) and section F-F.

NOTES : (1) Carry out the electrical bonding pr ocedure, method 3. Refer to the applicable Aircraft Maintenance Manual - Chapter 20-13-21 - Standard Practices - Airframe. (2) Apply aerodynamic sealant P/S 870-B1/2 along the contour of the hood assy. Refer to the applicable St ructural Repair Manual - Chapter 51-20-01 – Standard Practices and Structures - General. 10. Complete the application of fillet seal ant PN PR1440B2 (Spec. SAE AMS-S-8802 Type I Class B2) to the lightning diverter (4 positions). Refer to the applicable Structural Repair Manual – Chapter 51-20-01 – Standard Practices and Structures. Refer to detail A (POST MOD).
11. Measure the electrical resistance va lue between the lightning diverters and the primary structure. The maximum allowed re sistance value is 10 miliohms. Refer to the applicable Aircraft Maintenance M anual - Chapter 20-13-21 (TASK 20-13-21- 700-801- A) - Maintenance Practice s. Refer detail A (POST MOD).
12. Measure the electrical resistance value between the static discharger and the primary structure. The allowed resist ance value is from 6 megaohms to 150 megaohms. Refer to the applicable Airc raft Maintenance Manual - Chapter 20-13- 21 (TASK 20-13-21-700-801- A) - Maintenance Practices. Refer detail B (POST MOD).

- APPLICABLE TO GROUP 1
FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 02 OF 09)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 30 REVISION No.: Embraer Copyright © 2011. All rights reserved. 

### 13. Measure the electrical resistance value between the hood belt and the primary structure. The maximum allo wed resistance value is 10 miliohms. Refer to the applicable Aircraft Maintenance Manual - Chapter 20-13-21 (TASK 20-13-21-700- 801- A) - Maintenance Practices. Refer to detail B (POST MOD). 14. With a permanent marker pen or a rubber stamp, reidentify the movable Tail Boom fairing according to the Table, as follows:

REIDENTIFICATION TABLE
FROM TO
145-53615-403
145-21648-433
145-03536-401 145-03536-603

- APPLICABLE TO GROUP 1
FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 03 OF 09)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 31 Embraer Copyright © 2011. All rights reserved. 

### A ZONES

223 224

PRE − MOD



### DET. A

CONNECTOR P0708 (DISCONNECT)

CONNECTOR P0707 (DISCONNECT)

CONNECTOR P0715 (DISCONNECT) 2

2

2 GROMMET PN MS35489−8 (REMOVE AND DISCARD) 3 ELECTRICAL HARNESS W308 (REF.)



### DET. B **B**



### C

**C** 1

HOOD ASSY PN 145−23046−401 (REMOVE AND DISCARD)

1

EM145SB550326A.DGN SCREW PN PE21101−3−2CP (9 POSITIONS) (REMOVE AND DISCARD) CONNECTOR P0834 (REF.)

PRE − MOD

- APPLICABLE TO GROUP 1
FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 04 OF 09)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 32 REVISION No.: Embraer Copyright © 2011. All rights reserved. BONDING JUMPER PN PE88001−5AA6 (REMOVE AND DISCARD)

4 WASHER PN NAS1149FN416P (REMOVE AND DISCARD)

WASHER PN MS35338−40 (REMOVE AND DISCARD)

SCREW PN MS35206−216 (REMOVE AND DISCARD)

SCREW PN MS35206−214 (REMOVE AND DISCARD)

WASHER PN MS35338−40 (REMOVE AND DISCARD)

WASHER PN NAS1149FN416P (REMOVE AND DISCARD) WASHER PN NAS1197−4L (REMOVE AND DISCARD) NUT PN H14−04 (REMOVE AND DISCARD)

WASHER PN NAS1197−4L (REMOVE AND DISCARD)



## C−C
TYPICAL

PRE − MOD 4

4 4

4

4

4

4

4 4

EM145SB550327A.DGN

- APPLICABLE TO GROUP 1
FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 05 OF 09)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 33 Embraer Copyright © 2011. All rights reserved. 

### A ZONES

223 224



### DET. A

1

2 APPLY CYANOACRYLATE ADHESIVE PN SB496, OR SIMILAR. FILL GAPS AND FREE SPACES WITH SEALANT PN PR1776MB1/2, OR SIMILAR. 10 11

5

MOVABLE TAIL BOOM FAIRING (REIDENTIFY)

W308 (REF.)

CUT LINE GROMMET PN MS35489−8 (INSTALL) 1 2

EM145SB550328A.DGN LIGHTNING DIVERTER (4 POSITIONS) (APPLY FILLET SEALANT) (MEASURE THE ELECTRICAL RESISTANCE)

6 PRIMARY STRUCTURE (REF.)



### H

**G D** 

**B**

**DET. D** 

### F

**F**

POST − MOD ELECTRICAL HARNESS W308 (REROUTE)

14 CONNECTOR P0834 (REF.)

- APPLICABLE TO GROUP 1
FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 06 OF 09)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 34 REVISION No.: Embraer Copyright © 2011. All rights reserved. 3

4 ELECTRICAL BONDING (METHOD 3)
APPLY AERODYNAMIC SEALANT PN P/S870B−1/2 9 3 4 HOOD ASSY PN 145−23046−403 (INSTALL) 9

9 STATIC DISCHARGER (MEASURE THE ELECTRICAL RESISTANCE) CONNECTOR P0708 (INSTALL)

CONNECTOR P0707 (INSTALL) CONNECTOR P0715 (INSTALL) 8

8 8

EM145SB550329A.DGN SCREW PN PE21101−3−1CP (7 POSITIONS) (INSTALL)

SCREW PN PE21101−3−2CP (6 POSITIONS) (INSTALL) HOOD BELT (MEASURE THE ELECTRICAL RESISTANCE) 

### C

**C**

**DET. B**
POST − MOD 12

13

- APPLICABLE TO GROUP 1
FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 07 OF 09)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 35 Embraer Copyright © 2011. All rights reserved. TYPICAL 

### E **E**

BONDING JUMPER PN PE88001−5AA8 (INSTALL) 3

WASHER PN NAS1197−4L (INSTALL)

7 WASHER PN NAS1149FN416P (INSTALL)

7 WASHER PN MS35338−40 INSTALL)

7

SCREW PN MS35206−214 (INSTALL)

7

7
WASHER PN NAS1149FN416P (INSTALL)

WASHER PN NAS1197−4L (INSTALL) 7

SCREW PN MS24693−C6 (INSTALL)

7 7

NUT PN H14−04 (INSTALL) 7
WASHER PN MS35338−40 (INSTALL)



## E−E 7

ELECTRICAL BONDING (METHOD 3) 3 EM145SB550330A.DGN POST − MOD 

## C−C

- APPLICABLE TO GROUP 1
FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 08 OF 09)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 36 REVISION No.: Embraer Copyright © 2011. All rights reserved. EM145SB550357A.DGN HOOD ASSY

REAR MOVABLE FAIRING (REF.) DIVERTERS (REF.)

CLAMP PN PE27019R15 SCREW PN MS24694−C6 WASHER PN NAS1149FN832P NUT PN H14−08 (02 POSITIONS) (INSTALL)

5

5
CLAMP PN PE27019R15 SCREW PN NAS1801−08−8 WASHER PN NAS1149CN832R (INSTALL) 

## DET. H **DET. G** (TYPICAL) 

## SECTION F−F NUT PLATE (REF.)

- APPLICABLE TO GROUP 1
FIGURE 2: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 09 OF 09)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 37 Embraer Copyright © 2011. All rights reserved. 

### 1. Remove and discard hood assy PN 145-23046-401 by removing screw PN PE21101-3-2CP (9 positions). Re fer to detail B (PRE MOD).
2. Disconnect electrical connector P 0715 and splices SP7654, SP7655, and SP7656. Refer to detail B (PRE MOD). 3. Remove and discard grommet PN MS 35489-8. Refer to det ail A (PRE MOD). 4. Remove the bonding jumber (2 positions) attaching parts by removing screw PN MS35206-216, washer PN NAS11 49FN416P, PN MS35338-40, and PN NAS1197-4L (2 positions per bonding jumper), and nu t PN H14-04. Refer to SECTION C-C (PRE MOD).
5. Reroute electrical harness W308 and in stall clamp PN PE27019RI5 with screw PN NAS1801-08-8, washer PN NAS1149CN832R ,and clam p PN PE27019RI5 with screw PN MS24694-C6, washer PN NAS1149FN832 P, and nut PN H14-08. Refer to Details A (Post-Mod), G and H. 6. Install grommet PN MS35489-8 with cyanoac rylate adhesive PN SB496. Fill gaps and free spaces with sealant PN PR17 76M B1/2 654 SEMKIT (Spec AMS 3281, class B), or similar. Refer to detail D. 7. Install the bonding jumber (2 positions ) attaching parts using screw PN MS24693- C6, washer PN MS35338-40, PN NAS114 9FN416P, and PN N AS1197-4L, and nut PN H14-04. Refer to sections C-C and E-E.
NOTE : Carry out the electrical bonding pr ocedure, method 3. Refer to the applicable Aircraft Maintenance Manual - Chapter 20-13-21 - Standard Practices - Airframe.

- APPLICABLE TO GROUP 2
FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 01 OF 09)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 38 REVISION No.: Embraer Copyright © 2011. All rights reserved. 

### 8. Connect electrical connector P0715 and splices SP7654, SP7655, and SP7656. Refer to detail B (POST MOD). 9. Install hood assy PN 145-23046-403 between diverters and fairing with screw PN PE21101-3-1CP (7 positions) and PN PE21101-3-2CP (6 pos itions). Refer to detail B (POST MOD) and section F-F.
NOTES : (1) Carry out the electrical bonding pr ocedure, method 3. Refer to the applicable Aircraft Maintenance Manual - Chapter 20-13-21 - Standard Practices - Airframe. (2) Apply aerodynamic sealant P/ S870-B1/2 along the contour of the hood assy. Refer to the applicabl e Structural Repair Manual - Chapter 51-20-01 – Standard Practi ces and Structures - General. 10. Complete the application of fillet s ealant PN PR1440B2 (Spec. SAE AMS-S-8802 Type I Class B2) to the lightning diverter (4 positions). Refer to the applicable Structural Repair Manual – Chapter 51- 20-01 – Standard Practices and Structures. Refer to detail A (POST MOD).
11. Measure the electrical resistance va lue between the lightning diverters and the primary structure. The maxi mum allowed resistance value is 10 miliohms. Refer to the applicable Aircraft Maintenance Manual - Chapter 20-13-21 (TASK 20-13-21- 700-801- A) - Maintenance Practices and detail A (POST MOD).
12. Measure the electrical resistance value between the static discharger and the primary structure. The a llowed resistance value is from 6 mega ohms to 150 mega ohms. Refer to the applicable Aircraft Maintenance Manual - Chapter 20-13-21 (TASK 20-13-21-700-801- A) - Maintenance Practices and detail A (POST MOD).

- APPLICABLE TO GROUP 2
FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 02 OF 09)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 39 Embraer Copyright © 2011. All rights reserved. 

### 13. Measure the electrical resistance value between the hood belt and the primary structure. The maximum allo wed resistance value is 10 miliohms. Refer to the applicable Aircraft Maintenance Manual - Chapter 20-13-21 (TASK 20-13-21-700- 801- A) - Maintenance Practi ces and detail A (POST MOD). 14. With a permanent marker pen or a rubber stamp, reidentify t he movable Tail Boom fairing according to Table, as follows:

REIDENTIFICATION TABLE
FROM TO
145-03535-401 145-03535-603
145-03535-409 145-03535-617
145-38445-403
145-38445-407 145-03535-413

- APPLICABLE TO GROUP 2
FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 03 OF 09)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 40 REVISION No.: Embraer Copyright © 2011. All rights reserved. EM145SB550331A.DGN PRE − MOD



### DET. A

2

2 3



### DET. B **B**



### C

**C** 1

HOOD ASSY PN 145−23046−401 (REMOVE AND DISCARD)

1 CONNECTOR P0715 (DISCONNECT)

SPLICE SP7656 (DISCONNECT)

2
SPLICE SP7654 (DISCONNECT) 2
SPLICE SP7655 (DISCONNECT) ELECTRICAL HARNESS W308 (REF.) GROMMET PN MS35489−8 (REMOVE AND DISCARD)

SCREW PN PE21101−3−2CP (9 POSITIONS) (REMOVE AND DISCARD) 

### A ZONES

223 224

CONNECTOR P0834 (REF.)

PRE − MOD

- APPLICABLE TO GROUP 2
FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 04 OF 09)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 41 Embraer Copyright © 2011. All rights reserved. NUT PN H14−04 (REMOVE AND DISCARD)



## C−C
TYPICAL

PRE − MOD 4

4 BONDING JUMPER (REF.)

WASHER PN NAS1197−4L (REMOVE AND DISCARD) SCREW PN MS35206−216 (REMOVE AND DISCARD)

4

4

WASHER PN MS35338−40 (REMOVE AND DISCARD)

4
WASHER PN NAS1149FN416P (REMOVE AND DISCARD)

EM145SB550332A.DGN

- APPLICABLE TO GROUP 2 FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 05 OF 09)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 42 REVISION No.: Embraer Copyright © 2011. All rights reserved. 

### A ZONES

223 224



### DET. A

1

2 APPLY CYANOACRYLATE ADHESIVE PN SB496, OR SIMILAR. FILL GAPS AND FREE SPACES WITH SEALANT PN PR1776MB1/2, OR SIMILAR. 10 11

5

MOVABLE TAIL BOOM FAIRING (REIDENTIFY)

W308 (REF.)

CUT LINE GROMMET PN MS35489−8 (INSTALL) 1 2 LIGHTNING DIVERTER (4 POSITIONS) (APPLY FILLET SEALANT) (MEASURE THE ELECTRICAL RESISTANCE)

6

EM145SB550333A.DGN POST − MOD PRIMARY STRUCTURE (REF.) 

### D

**B** 

### F

**F**

**DET. D H** 

**G** ELECTRICAL HARNESS W308 (REROUTE)

14 CONNECTOR P0834 (REF.)

- APPLICABLE TO GROUP 2
FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 06 OF 09)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 43 Embraer Copyright © 2011. All rights reserved. 3

4 ELECTRICAL BONDING (METHOD 3)
APPLY AERODYNAMIC SEALANT PN P/S870B−1/2 9 3 4 HOOD ASSY PN 145−23046−403 (INSTALL) 9

9 STATIC DISCHARGER (MEASURE THE ELECTRICAL RESISTANCE)

8 8

SPLICE SP7655 (CONNECT)

8
SPLICE SP7656 (CONNECT) 8
SPLICE SP7654 (CONNECT) CONNECTOR P0715 (CONNECT)

EM145SB550344A.DGN HOOD BELT (MEASURE THE ELECTRICAL RESISTANCE) SCREW PN PE21101−3−1CP (7 POSITIONS) (INSTALL)

SCREW PN PE21101−3−2CP (6 POSITIONS) (INSTALL)

POST − MOD 

### C

**C**

**DET. B** 12

13

- APPLICABLE TO GROUP 2
FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 07 OF 09)

# SERVICE BULLETIN

SB No.: 145LEG-55-0013 DATE: 08/Sep/2011 PAGE: 44 REVISION No.: Embraer Copyright © 2011. All rights reserved. EM145SB550345A.DGN TYPICAL 

### E **E**

3

7
WASHER PN NAS1149FN416P (INSTALL)

WASHER PN NAS1197−4L (INSTALL) 7

SCREW PN MS24693−C6 (INSTALL)

7 7

NUT PN H14−04 (INSTALL) 7
WASHER PN MS35338−40 (INSTALL)



## E−E

ELECTRICAL BONDING (METHOD 3) 3 BONDING JUMPER (REF.)

POST − MOD 

## C−C

- APPLICABLE TO GROUP 2
FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 08 OF 09)

# SERVICE BULLETIN

DATE: 08/Sep/2011 SB No.: 145LEG-55-0013 REVISION No.: PAGE: 45 Embraer Copyright © 2011. All rights reserved. HOOD ASSY

REAR MOVABLE FAIRING (REF.) DIVERTERS (REF.)

CLAMP PN PE27019R15 SCREW PN MS24694−C6 WASHER PN NAS1149FN832P NUT PN H14−08 (02 POSITIONS) (INSTALL)

5

5
CLAMP PN PE27019R15 SCREW PN NAS1801−08−8 WASHER PN NAS1149CN832R (INSTALL) 

## DET. H **DET. G** (TYPICAL) 

## SECTION F−F

EM145SB550358A.DGN NUT PLATE (REF.)

- APPLICABLE TO GROUP 2
FIGURE 3: IMPROVEMENT IN THE LIGHTNING PROTECTION OF THE ELECTRICAL SYSTEM (SHEET 09 OF 09). . .



### SERVICE BULLETIN IMPLEMENTATION AND EVALUATION FORM
The purpose of this form is to collect data that will be used to improve the quality of our Service Bulletins and Reliability Program. Please fill in this form and return it to: EMBRAER S.A. Customer Support Contact Center Embraer Executive Jets contact.center@embraer.com
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SB Number/Revision: SB Title: SB145LEG-55-0013R00 IMPROVEMENT IN THE LIGH TNING PROTECTION OF THE TAIL BOOM
SB Implementation Report Aircraft Serial Number or Registration Number: Incorporation Date:
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SB Evaluation (Check applicable squares below) Estimated Manpower: [ ] OK [ ] Not OK (Explain below) Material & Kits: [ ] OK [ ] Not OK (Explain below) Accomplishment Instructions: [ ] OK [ ] Not OK (Explain below) Figures: [ ] OK [ ] Not OK (Explain below) SB General Evaluation: [ ] OK [ ] Not OK (Explain below) Comments: (Bulletin quality, difficulties found at the ti me of incorporation, suggested improvements,...)

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E-mail: Prepared by: (Name/Title) Date:

ENS-003393